Earticle

초록

영어

Leading edge icing jeopardizes the aerodynamic performance of wing and the fly safety of airplane. Macro fiber composite(MFC) piezoelectric actuator possess favorable flexibility and large force output ability, which makes MFC quite suitable for the excitation of large curvature thin-walled structures such as wing leading edge. In this study, MFC is adopted for leading edge in flight deicing application. Key challenges of leading edge in flight deicing with MFC were investigated by finite element methodology and simulation approach, which include fundamental analysis of vibration deicing method, leading edge deicing excitation mode and MFC placement scheme determination. Base on thermal-elastic analogy modeling theory, asymmetric temperature load modeling method is proposed for the special actuation effect simulation of twist type MFC for deicing. Simulation results demonstrate the third natural vibration mode can be utilized for leading edge deicing with lowest energy consumption and twist type MFC has great potential for leading edge in flight deicing application.

목차

Abstract
 1. Introduction
 2. Fundamental of Leading Edge Deicing by Structure Vibration
  2.1. Leading edge structure modeling for deicing analysis
  2.2. Leading edge structure modeling with ice
 3. Energy Consumption Analysis and Key Parameter Optimization
 4. MFC Excited Vibration Deicing Method Simulation
 5. Conclusion
 Acknowledgements
 References

키워드

저자

• Wei Wang [ Department of Aerospace Structure Engineering, School of Aeronautics, Northwestern Polythechnical University, Xi’an 710072, China ]
• Zhichun Yang [ Department of Aerospace Structure Engineering, School of Aeronautics, Northwestern Polythechnical University, Xi’an 710072, China ]

참고문헌

발행기관

간행물

표지보기 관심저널 등록

• 간행물명

  International Journal of Control and Automation

• 간기

  월간

• pISSN

  2005-4297

• 수록기간

  2008~2016

• 십진분류

  KDC 505 DDC 605